Using several known facts about the rocket and the Estes B6 engine, we were able to calculate estimates for the rocket's performance. These do not account for factors such as drag, wind, or non-verticality of launch.
Maximum velocity
M (mass of rocket) = 110g = 0.11kg
Fa (B6 avg. thrust) = 6N
T (B6 burn time) = 0.85s
V1 = 0
V2 = ?
A = ?
D1 (distance under power) = ?
Fg = MA
Fg = 0.11(9.8)
Fg = 1.1N
Fnet = Fa - Fg Fnet = 4.9N
F = MA
4.9 = 0.11A A = 45 m/s^2
V2 = V1 + AT
V2 = 0 + 45(0.85) V2 = 38 m/s
Maximum velocity of 38 m/s will occur just as the fuel is exhausted.
Performance Projections
Using several known facts about the rocket and the Estes B6 engine, we were able to calculate estimates for the rocket's performance. These do not account for factors such as drag, wind, or non-verticality of launch.
Maximum velocity
M (mass of rocket) = 110g = 0.11kgFa (B6 avg. thrust) = 6N
T (B6 burn time) = 0.85s
V1 = 0
V2 = ?
A = ?
D1 (distance under power) = ?
Fg = MA
Fg = 0.11(9.8)
Fg = 1.1N
Fnet = Fa - Fg
Fnet = 4.9N
F = MA
4.9 = 0.11A
A = 45 m/s^2
V2 = V1 + AT
V2 = 0 + 45(0.85)
V2 = 38 m/s
Maximum velocity of 38 m/s will occur just as the fuel is exhausted.
V2^2 = V1^2 + 2AD
1444 = 0 + 2(45)D1
1444 = 90D1
D1 = 16m
Maximum Altitude
V1 = 38 m/sV2 = 0
Ag = -9.8 m/s^2
D1 = 16m
D2 (distance coasting) = ?
D (max. altitude) = ?
V2^2 = V1^2 + 2AD
0 = 1444 + 2(-9.8)D2
19.6D2 = 1444
D2 = 74m
D = D1 + D2
D = 90m
Assuming vertical launch and no air resistance, the rocket should achieve 38m/s max. velocity and a 90m apogee.
λ - Design - Performance Projections- Materials - Time LinePrimary Launch - Secondary launch - Analysis - ConclusionLab Report